Taepo Dong-2 IRBM VARIANT(S) AND/OR ALTERNATE NAME(S):
---- No Dong-3 IRBM (alternate designation)
---- Hwasong-2 IRBM (alternate designation)
---- Moksong-2 IRBM (alternate designation)
---- Shahab-5 IRBM (Iranian designation)
EQUIPMENT CATEGORY: Missiles/Rockets/Bombs -- Land Attack/Theater
Nuclear/Biological/Chemical -- Nuclear
COUNTRY OF ORIGIN: North Korea PICTURES OF: Taepo Dong-2 IRBM
DESCRIPTION
The Taepo Dong-2 (TD-2) is an intermediate-range ballistic missile (IRBM), alternatively called the No Dong-3, Hwasong-2 and Moksong-2. The U.S. intelligence community uses the designation Taepo Dong-2. There is also a probable space-launch vehicle (SLV) based on the Taepo Dong-2.
As does the Taepo Dong-1, the Taepo Dong-2 consists of two stages (though some analyses have posited a possible third stage). The first stage may be a modified version of China's DF-3 (CSS-2, Dong Feng 3) missile. The second stage is possibly North Korea's No Dong missile. Both stages use storable TM-185 liquid propellant using an AK-27I oxidizer. Unlike the Taepo Dong-1, the first stage uses four separate No Dong motors, each with one thrust chamber. Some analysts believe the design will have characteristics similar, but somewhat inferior, to the Soviet-built SS-5 .
The stages of the Taepo Dong-2 use liquid rocket engines with a propellant combination of inhibited red fuming nitric acrid (IRFNA) and kerosene. Ignition is accomplished with a self-igniting fuel.
The propellant feed system is a turbo pump driven by a bipropellant gas generator using the main propellants. The startup and shutdown valves are one-shot devices that are actuated by pyrotechnic charges. Tank pressurization is accomplished by using air stored in a high-pressure bottle heated by th e turbine exhaust gases.
The missile's guidance depends on it being orientated prior to launch on a trajectory aimed at the target; the guidance systems keeps the missile in this plane. Two of the three body-mounted gyros are used for attitude. The third gyro is for lateral acceleration control. A pendulum integration gyro assembly measures speed. The fins are fixed and thrust vector control is accomplished by four jet vanes.
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